2026-03-09T20:55:57Z https://jaxa.repo.nii.ac.jp/oai

oai:jaxa.repo.nii.ac.jp:00033255 2023-06-21T00:11:53Z 1887:1890 1896:1898:1899:1991

Thermal Protection System of the Reentry Capsule with Superorbital Velocity 山田, 哲哉 石井, 信明 稲谷, 芳文 本田, 雅久 Yamada, Tetsuya Ishii, Nobuaki Inatani, Yoshifumi Honda, Masahisa In the final phase of the MUSES-C mission, a small capsule with asteroid sample conducts reentry flight directly from the interplanetary transfer orbit at the velocity over 12 km/s. The severe heat flux, the complicated functional requirements, and small weight budget impose several engineering challenges on the designing of the thermal protection system of the capsule. The heat shield is required to function not only as ablator but also as a structural component. The cloth-layered carbon-phenolic ablator, which has higher allowable stress, is developed in newly devised fabric method for avoiding delamination due to the high aerodynamic heating. The ablation analysis code, which takes into account of the effect of pyrolysis gas on the surface recession rate, has been developed and verified in the arc-heating tests in the facility environment of broad range of enthalpy level. The capsule was designed to be ventilated during the reentry flight up to about atmospheric pressure by the time of parachute deployment by being sealed with porous flow-restrict material. The designing of the thermal protection system, the hardware specifications, and the ground-based test programs of MUSES-C capsule are summarized and discussed here in this paper. 資料番号: SA0200028000 departmental bulletin paper 宇宙科学研究所 Institute of Space and Astronautical Science 2003-03 application/pdf The Institute of Space and Astronautical Science report. S.P. : Aerodynamics, Thermophysics, Thermal Protection, Flight System Analysis and Design of Asteroid Sample Return Capsule 17 245 261 0288-433X AA10455137 https://jaxa.repo.nii.ac.jp/record/33255/files/SA0200028.pdf https://jaxa.repo.nii.ac.jp/records/33255 eng